Method of machining slots in a turbine disk of a turbine engine

Abstract

A machining method for machining peripheral slots in a disk of a turbine of a turbine engine, such as an airplane turboprop or turbojet, the method including: machining the slots by reaming using a substantially cylindrical reamer of length greater than an axial thickness of the disk, and extending substantially parallel to the axis of the disk, outlines of the slots being machined by moving the reamer perpendicularly to its axis along the profile of each slot.

1 - 12 . (canceled) 
     
     
         13 . A machining method for machining peripheral slots in a turbine disk of a turbine engine, or an airplane turboprop or turbojet, the method comprising:
 machining the slots by reaming using a substantially cylindrical reamer of length greater than an axial thickness of the disk; and   extending outlines of the slots substantially parallel to the axis of the disk, the outlines of the slots being machined by moving the reamer perpendicularly to its axis along the profile of each slot.   
     
     
         14 . A machining method according to  claim 13 , wherein the direction of rotation of the reamer is such that the reaming is performed by climb milling, and a direction of advance of teeth of the reamer corresponds to a direction of advance of the reamer relative to the material that is to be machined. 
     
     
         15 . A machining method according to  claim 13 , wherein the turbine disk is a low pressure turbine disk. 
     
     
         16 . A method according to  claim 13 , wherein the disk is made of nickel-based alloy. 
     
     
         17 . A machining method according to  claim 13 , wherein the reamer is held at each of its ends by a tool support, at least one of the ends of the reamer being driven in rotation by drive means. 
     
     
         18 . A machining method according to  claim 13 , wherein the reamer is made of tungsten carbide or of high-speed steel. 
     
     
         19 . A machining method according to  claim 13 , wherein the reamer has two to eight teeth, and a helix angle of the reamer, which is an angle between the axis of the reamer and inclination of the teeth, is in a range of 10° to 20°. 
     
     
         20 . A machining method according to  claim 13 , wherein the cutting speed of the reamer lies in a range of 40 in/min to 70 m/min. 
     
     
         21 . A machining method according to  claim 13 , further comprising at least a blanking stage and a finishing stage. 
     
     
         22 . A turbine of a turbine engine of an airplane turboprop or turbojet, comprising at least one disk machined by performing the method according to  claim 13 . 
     
     
         23 . A reaming tool, or a reaming tool for machining peripheral slots in a turbine disk of a turbine engine, the tool comprising:
 a reamer support with two parallel arms, each having an end including a respective end of a reamer; and   means for driving at least one of the ends of the reamer in rotation.   
     
     
         24 . A reaming tool according to  claim 23 , wherein the reamer is cylindrical.